[Federal Register Volume 59, Number 131 (Monday, July 11, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-16399]


[[Page Unknown]]

[Federal Register: July 11, 1994]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-ANE-27; Amendment 39-8964; AD 94-14-16]

 

Airworthiness Directives; Pratt & Whitney JT8D Series Turbofan 
Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Pratt & Whitney (PW) JT8D series engines. This 
action requires initial and repetitive inspections of the Number 7 fuel 
nozzle and support assembly, replacement of the Number 7 fuel nozzle 
and support assembly with a more leak-resistant configuration, and 
replacement of aluminum oil pressure and scavenge tube fittings with 
steel fittings. This amendment is prompted by reports of two engine 
fires initiated by fuel leakage from the Number 7 fuel nozzle and 
support assembly, ignition of that fuel, melting of aluminum oil 
pressure and scavenge tube fittings that are in the proximity of the 
Number 7 nozzle, and augmentation of that fire with the liberated oil. 
The actions specified in this AD are intended to prevent fuel leakage 
from the Number 7 fuel nozzle and support assembly, ignition of that 
leaking fuel, and liberation of oil from melted oil line fittings, 
which can result in an uncontained engine fire and damage to the 
aircraft.

DATES: Effective July 26, 1994.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 26, 1994.
    Comments for inclusion in the Rules Docket must be received on or 
before September 9, 1994.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket Number 94-ANE-27, 12 New England 
Executive Park, Burlington, MA 01803-5299.
    The service information referenced in this AD may be obtained from 
Pratt & Whitney, Technical Publications Department, M/S 132-30, 400 
Main Street, East Hartford, CT 06108. This information may be examined 
at the FAA, New England Region, Office of the Assistant Chief Counsel, 
12 New England Executive Park, Burlington, MA; or at the Office of the 
Federal Register, 800 North Capitol Street NW., suite 700, Washington, 
DC.

FOR FURTHER INFORMATION CONTACT: Mark A. Rumizen, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (617) 
238-7137, fax (617) 238-7199.

SUPPLEMENTARY INFORMATION: The Federal Aviation Administration (FAA) 
has received two reports of uncontained engine fires on Pratt & Whitney 
(PW) JT8D series engines due to fuel leakage from the Number 7 fuel 
nozzle and support assembly, ignition of that fuel, melting of aluminum 
oil pressure and scavenge tube fittings that are in the proximity of 
the Number 7 nozzle, and augmentation of that fire with the liberated 
oil. The resulting fire burned through the engine diffuser case and fan 
ducts, causing an aircraft engine cowl fire. The FAA has determined 
that the fuel nozzle and support assembly is susceptible to incomplete 
or improper refurbishment or repair that could result in fuel leaks 
across the fuel nozzle seals, and that the aluminum oil pressure and 
scavenge tube fittings have inadequate fire resistance capability. 
These oil line fittings are in the path of the fuel leaking and 
associated fire from the Number 7 fuel nozzle and support assembly. 
Impingement of the fire on these oil fittings causes them to melt, thus 
causing the oil contained in the oil tubes to escape and to augment the 
fire. Therefore, this amendment will require the inspection of the 
Number 7 fuel nozzle and support assembly for evidence of fuel leakage 
and burning until replacement of the Number 7 fuel nozzle and support 
assembly with a more leak-resistant configuration. It also requires 
replacement of the aluminum oil tube fittings with steel fittings. This 
condition, if not corrected, could result in fuel leakage from the 
Number 7 fuel nozzle and support assembly, ignition of that leaking 
fuel, and liberation of oil from melted oil line fittings, which can 
result in an uncontained engine fire and damage to the aircraft.
    The FAA has reviewed and approved the technical contents of PW 
Alert Service Bulletin (ASB) No. A6153, Revision 1, dated June 8, 1994, 
that describes procedures for initial and repetitive borescope 
inspections of the Number 7 fuel nozzle and support assembly; and ASB 
No. A6169, Revision 1, dated June 15, 1994, and A6170, dated May 13, 
1994, that describe procedures for replacement of the Number 7 fuel 
nozzle and support assembly with a more leak-resistant configuration 
and replacement of the aluminum oil tube fittings with steel fittings, 
respectively.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other PW JT8D series engines of the same type 
design, this AD is being issued to prevent uncontained engine fire and 
damage to the aircraft. This AD requires inspection of the Number 7 
fuel nozzle and support assembly for evidence of fuel leakage and 
burning until replacement of the Number 7 fuel nozzle and support 
assembly with an improved sealing configuration. This AD also requires 
replacement of the aluminum oil tube fittings with steel fittings. The 
actions are required to be accomplished in accordance with the alert 
service bulletins described previously.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications should identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 94-ANE-27.'' The postcard will be date stamped and 
returned to the commenter.
    The regulations adopted herein will not have substantial direct 
effects on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and is not a ``significant regulatory action'' 
under Executive Order 12866. It has been determined further that this 
action involves an emergency regulation under DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979). If it is determined 
that this emergency regulation otherwise would be significant under DOT 
Regulatory Policies and Procedures, a final regulatory evaluation will 
be prepared and placed in the Rules Docket. A copy of it, if filed, may 
be obtained from the Rules Docket at the location provided under the 
caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

94-14-16  Pratt & Whitney: Amendment 39-8964. Docket 94-ANE-27.

    Applicability: Pratt & Whitney (PW) Model JT8D-209, -217, -217A, 
-217C, -219 turbofan engines; and JT8D-1, -1A, -1B, -7, -7A, -7B, -
9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR turbofan engines 
incorporating the original issue or any revision of Pratt & Whitney 
Service Bulletin No. 5650; and any PW Model JT8D engine with low 
emissions fuel nozzles, Part Numbers 775485, 809137-01, 802965, and 
5004308-02 installed. These engines are installed on but not limited 
to Boeing 727 and 737 series, and McDonnell Douglas DC-9 and MD-80 
series aircraft.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent fuel leakage from the Number 7 fuel nozzle and 
support assembly and melting of the oil pressure and scavenge tube 
fittings, which can result in an uncontained engine fire and damage 
to the aircraft, accomplish the following:
    (a) Inspect Number 7 fuel nozzle and support assemblies in 
accordance with PW Alert Service Bulletin (ASB) No. A6153, Revision 
1, dated June 8, 1994, as follows:
    (1) For Number 7 fuel nozzle and support assemblies that have 
accumulated more than 2,500 hours time in service (TIS) since last 
fuel nozzle and support assembly overhaul on the effective date of 
this airworthiness directive (AD), initially inspect for fuel 
leakage within 700 hours TIS after the effective date of this AD.
    (2) For engines with Number 7 fuel nozzle and support assemblies 
with 2,500 or less hours TIS since fuel nozzle and support assembly 
overhaul on the effective date of this AD, initially inspect prior 
to accumulating 3,200 hours TIS since overhaul.
    (3) Thereafter, inspect for fuel leakage in accordance with PW 
ASB A6153, Revision 1, dated June 8, 1994, at intervals not to 
exceed 700 hours TIS since last inspection.
    (4) Remove from service Number 7 fuel nozzle and support 
assemblies that exhibit evidence of fuel leakage as described in PW 
ASB No. A6153, Revision 1, dated June 8, 1994, and replace with the 
improved sealing configuration nozzle in accordance with paragraph 
(b) of this AD, as follows:
    (i) Within 25 hours TIS, or 25 cycles in service (CIS), 
whichever occurs first, after the inspection performed in paragraph 
(a)(1), (a)(2), or (a)(3) for aircraft with only one engine 
exhibiting Number 7 fuel nozzle and support assembly leakage.
    (ii) Prior to further flight, on aircraft with two engines 
exhibiting Number 7 fuel nozzle and support assembly leakage, remove 
and replace at least one of the leaking Number 7 fuel nozzle and 
support assemblies. The remaining Number 7 fuel nozzle and support 
assembly that exhibits leakage shall be removed and replaced in 
accordance with paragraph (a)(4)(i) of this AD.
    (iii) Prior to further flight, on Boeing 727 aircraft, with 
three engines exhibiting Number 7 fuel nozzle and support assembly 
leakage, remove and replace at least two of the leaking Number 7 
fuel nozzle and support assemblies. The remaining Number 7 fuel 
nozzle and support assembly that exhibits leakage shall be removed 
and replaced in accordance with paragraph (a)(4)(i) of this AD.
    Note: Fuel nozzles that have not undergone overhaul do not 
require inspection in accordance with paragraph (a) of this AD.

    (b) At the next accessibility of the diffuser build group after 
the effective date of this AD, but no later than July 31, 1999, 
accomplish the following:
    (1) Replace the Number 7 fuel nozzle and support assembly with 
the improved sealing configuration in accordance with Part 1 of PW 
ASB No. A6169, Revision 1, dated June 15, 1994.
    (2) Replace the aluminum pressure and scavenge oil tube fittings 
with steel fittings in accordance with PW ASB No. A6170, dated May 
13, 1994.

    Note: Replacement of the following oil tubes with corresponding 
oil tubes that incorporate steel fittings constitutes compliance 
with paragraph (b)(2) of this AD:

    (i) Outer internal Number 4 and 5 bearing pressure tube assembly 
for PW JT8D-200 series engines.
    (ii) Outer internal main bearing pressure tube assembly for PW 
JT8D-200 series engines.
    (iii) Main bearing pressure manifold assembly for PW JT8D-200 
series engines.
    (iv) Front Number 4\1/2\ and 6 bearing pressure tube assembly 
for all other JT8D engines.
    (v) Number 4 bearing oil scavenge tube assembly for all other 
JT8D engines.
    (vi) Number 4 bearing oil pressure tube assembly for all other 
JT8D engines.
    (vii) Main bearing pressure manifold assembly for all other JT8D 
engines.

    (c) Incorporation of the hardware required by paragraph (b)(1) 
of this AD, constitutes terminating action for the inspections 
required by paragraph (a) of this AD.
    (d) For the purpose of this AD, accessibility of the diffuser 
build group is defined as engine maintenance that entails flange 
separation of the diffuser case from the combustion chamber outer 
case.
    (e) For the purpose of this AD, fuel nozzle and support assembly 
overhaul is defined as disassembly of the fuel nozzle from the 
support assembly that entails removal of the fuel nozzle nut.
    (f) For any Number 7 fuel nozzle and support assembly that is 
removed for evidence of leakage in accordance with paragraph (a) of 
this AD, submit the following information within 60 days after the 
removal, to the Manager, Engine Certification Office, Engine and 
Propeller Directorate, Aircraft Certification Service, FAA, 12 New 
England Executive Park, Burlington, Massachusetts, 01803-5299; fax 
(617) 238-7199:
    (1) Fuel nozzle and support assembly part number and serial 
number.
    (2) Fuel nozzle and support assembly time and cycles since 
overhaul.
    (3) Description of fuel nozzle and support assembly distress.
    (4) Position of distressed fuel nozzle and support assembly.
    (5) Description of any other resultant engine damage.
    (6) Engine serial number.
    (7) Engine time and cycles since overhaul.
    The reporting requirements of this AD terminate after compliance 
with paragraph (b)(1) of this AD. Information collection 
requirements contained in this regulation have been approved by the 
Office of Management and Budget (OMB) under the provision of the 
Paperwork Reduction Act of 1980 (44 U.S.C. 3501-3520) and have been 
assigned OMB Control Number 2120-0056.
    (g) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Engine Certification Office. The 
request should be forwarded through an appropriate FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Engine Certification Office.

    Note: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the Engine Certification Office.

    (h) Special flight permits may be issued in accordance with 
Sec. Sec. 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the aircraft to a location where 
the requirements of this AD can be accomplished.
    (i) The inspections and modifications shall be done in 
accordance with the following service documents: 

------------------------------------------------------------------------
       Document No.          Pages     Revision             Date        
------------------------------------------------------------------------
PW ASB No. A6153..........   1-4     1...........  June 8, 1994.        
                               5     Original....  February 4, 1994.    
                             6-8     1...........  June 8, 1994.        
                            9-12     Original....  February 4, 1994.    
Total pages: 12.                                                        
PW ASB No. A6169..........   1-6     1...........  June 15, 1994.       
                            7-16     Original....  April 29, 1994.      
                              17     1...........  June 15, 1994.       
                            1-30     Original....  April 29, 1994.      
Total pages: 30.                                                        
PW ASB No. A6170..........  1-20     Original....  May 13, 1994.        
Total pages: 20.                                                        
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    This incorporation by reference was approved by the Director of 
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51. Copies may be obtained from Pratt & Whitney, Technical 
Publications Department, M/S 132-30, 400 Main Street, East Hartford, 
CT 06108. Copies may be inspected at the FAA, New England Region, 
Office of the Assistant Chief Counsel, 12 New England Executive 
Park, Burlington, MA; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.
    (j) This amendment becomes effective on July 26, 1994.

    Issued in Burlington, Massachusetts, on June 29, 1994.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 94-16399 Filed 7-8-94; 8:45 am]
BILLING CODE 4910-13-P